CN111976951A

CN111976951A - Aircraft window and aircraft window display

Info

Publication number: CN111976951A
Application number: CN202010443820.3A
Authority: CN
Inventors: 史蒂芬·斯宾塞; 西恩·索恩顿; 约翰·布洛克; 蒂莫西·奥哈拉; 马修·***; 布莱恩·布里斯科
Original assignee: Gulfstream Aerospace Corp
Current assignee: Gulfstream Aerospace Corp
Priority date: 2019-05-24
Filing date: 2020-05-22
Publication date: 2020-11-24
Anticipated expiration: 2040-05-22
Also published as: US11390370B2; US11685505B2; CN111976951B; US20230278693A1; EP3741663B1; US20220281581A1; KR20200135741A; EP3741663A1; US20200369361A1; KR102606974B1

Abstract

A sidewall assembly for an aircraft and an aircraft are provided. In one example, the sidewall assembly includes a window. The sidewall portion has an inward side and at least partially surrounds the window. A transparent display panel is coupled to the sidewall portion and covers the inward facing side of the sidewall portion including the window. The transparent display panel includes a display screen configured to display information to a passenger. The display controller communicates with the transparent display panel to transmit video/audio signals providing the information to the display screen.

Description

Aircraft window and aircraft window display

Cross Reference to Related Applications

The present application is a partial Continuation In Part (CIP) application of us application 16/421,891 filed 24.5.2019, the entire contents of which are incorporated herein by reference.

Technical Field

The present disclosure relates to a sidewall including an aircraft window, and more particularly to a sidewall construction including an aircraft window with an integrated display unit.

Background

This section provides background information related to the present disclosure that is not necessarily prior art.

The desire to enhance entertainment for aircraft passengers has led to an increase in the number of screens used by passengers to provide on-demand content. The increase in these screens increases the weight of the aircraft, thereby compromising the fuel economy of the aircraft. Accordingly, it is desirable to provide a mechanism that reduces the added weight without reducing the passenger's access to on-demand content.

Disclosure of Invention

Various non-limiting embodiments of a sidewall assembly for an aircraft are provided herein, as well as various non-limiting embodiments of an aircraft.

In a first non-limiting embodiment, the sidewall assembly includes, but is not limited to, a window. The sidewall assembly also includes, but is not limited to, a sidewall portion having an inwardly facing side and at least partially surrounding the window. The sidewall assembly also includes, but is not limited to, a transparent display panel coupled to the sidewall portion and covering the inward facing side of the sidewall portion including the window. The transparent display panel includes a display screen configured to display information to a passenger. The sidewall assembly also includes, but is not limited to, a display controller in communication with the transparent display panel to transmit video/audio signals providing the information to the display screen.

In another non-limiting embodiment, the aircraft includes, but is not limited to, a fuselage that encloses an aircraft interior. The fuselage includes a sidewall portion having an inwardly facing side disposed adjacent the aircraft interior. The aircraft also includes, but is not limited to, a window disposed in the fuselage and at least partially surrounded by the sidewall portion. The aircraft also includes, but is not limited to, a transparent display panel coupled to the sidewall portion and covering the inward facing side of the sidewall portion including the window. The transparent display panel includes a display screen configured to display information to passengers of the aircraft interior. The aircraft also includes, but is not limited to, a display controller in communication with the transparent display panel to transmit video/audio signals providing the information to the display screen.

Drawings

The drawings described herein are for illustrative purposes only of selected embodiments and not all possible implementations, and are not intended to limit the scope of the present disclosure.

FIG. 1 is a perspective view illustrating an aircraft having a window in accordance with an exemplary embodiment;

FIG. 2 is a perspective view illustrating an aircraft interior panel including two windows in accordance with an exemplary embodiment;

FIG. 3 is a front view of a window according to an exemplary embodiment;

FIG. 4 is an exploded view of a window according to an exemplary embodiment;

fig. 5 is a sectional view showing a section of the window of fig. 1 to 4;

FIG. 6 is a perspective view illustrating an aircraft interior including a sidewall assembly including a transparent display panel having a plurality of display screens in accordance with an exemplary embodiment;

FIG. 7 is a side view of a sidewall assembly for an aircraft in accordance with an exemplary embodiment;

FIG. 8 is a perspective view of a sidewall assembly for an aircraft in accordance with an exemplary embodiment;

FIG. 9 is a perspective view of a sidewall assembly for an aircraft in accordance with an exemplary embodiment;

FIG. 10 is a cross-sectional view of the sidewall assembly shown in FIG. 7 along line 10-10;

FIG. 11 is a cross-sectional view of the sidewall assembly shown in FIG. 7, taken along line 11-11;

FIG. 12 is an enlarged cross-sectional view of the encircled area 12 of the sidewall assembly shown in FIG. 10;

FIG. 13 is an enlarged cross-sectional view of encircled area 13 of the sidewall assembly shown in FIG. 11; and

FIG. 14 is a block diagram of a transparent display panel having multiple display screens in communication with a display controller and other systems according to an example embodiment.

Corresponding reference characters indicate corresponding parts throughout the several views of the drawings.

Detailed Description

Exemplary embodiments will now be described more fully with reference to the accompanying drawings. Fig. 1 and 2 each illustrate an aircraft 10 according to the present teachings, the aircraft 10 including a fuselage 100 having a window display 12 and an associated passenger cabin interior panel 11. The window display 12 is configured to be positioned between an exterior window component 14 of an aircraft cabin 16 and an interior cabin window 18. The window display 12 is configured to provide textual or graphical information to passengers within the passenger compartment 16. As described below, the display 12 may be removably secured to the interior passenger compartment window 18 for repair or replacement. The passenger compartment interior panel 11 may include switches or capacitive sensors (not shown) that allow passengers to interface with the contents of the display 12.

The display 12 includes a transparent (e.g., translucent) display member 20 (see fig. 3) for communicating information to the occupant. The transparent display member 20 may be a thin film transparent display member such as an LCD display or a transparent thin film with associated OLEDs. Additionally, display member 20 may be an associated projection display along a frame of the display member. The thin film transparent display 20 has controllable data transmission circuitry 22 for varying the transmission of light through or from pixels 24 defined in the thin film transparent display member 20 (see fig. 3).

As best shown in fig. 3, the controllable data transmission circuit 22 has a plurality of associated sensors (26, 28, 30) that can be used to vary the color or amount of light transmitted through each pixel associated with the image 32. Alternatively, the color or amount of light associated with the background 34 of the display member 20 may be automatically changed to maximize visibility. The amount of backlight that passes through the outer window section 14 at any given time varies greatly due to differences in the elevation and position of the sun with respect to the earth. Due to changes in environmental conditions, the associated sensor 30 may be a temperature measurement sensor that allows the circuit 22 to vary the current to the display member as needed to maintain visual quality or protect the thin film display.

In addition, since the cabin lighting may change during the flight, the visibility of the information transmitted by the display member 20 to the passengers may become unclear. Accordingly, the circuit 22 may include a pair of light receiving sensors 26, 28 that determine the amount of light passing through the window assembly and the interior passenger compartment. Both sensors 26, 28 provide signals indicative of these light values. The controllable data transmission circuit 22 then calculates the difference in the amount of light between the cabin interior and the cabin exterior and adjusts the darkness or color of the pixel sending the transmission information or adjusts the amount of light transmitted through the background.

In the case of an OLED display, the amount of light transmitted by the OLED may be adjusted to adjust the current or voltage of the OLED to change the visibility of the pixels transmitting the information or the temperature of the thin film display. Additionally, display member 20 may incorporate a capacitive touch sensor that allows a passenger to interact with window display 12 to change the image on display 12. These touch sensors may use the electrodes of the OLEDS to convert the display member into a capacitive touchpad.

Alternatively, the thin display member 20 may include a second layer of LCD or a polarisable material (not shown) that can vary the overall amount of light transmitted through the interior passenger compartment window 18. It is contemplated that the display member 20 may be used to convey safety information to the occupant, such as the need to remain seated or to fasten a seat belt. Additionally, as shown in FIG. 3, information relating to the location of the aircraft along the flight path, ground or air visuals of interest, or movies may be shown.

FIG. 4 shows an exploded view of a window according to the present teachings. There is shown an associated cabin interior panel 11 which may be in the form of a wall panel or window frame. As shown, the window display 12 is positioned between an exterior window component 14 of an aircraft cabin 16 and an interior cabin window 18. To facilitate maintenance, the display 12 may be removably secured to the interior passenger compartment window 18 for easy access.

Fig. 5 shows a cross section of an aircraft window with a display member 20. The exterior window assembly 14 and the passenger interior window 18 may have a curved or flat configuration (i.e., a planar or substantially planar cross-sectional shape). The exterior surface 40 of the cabin interior window 18 and the exterior window component 14 are spaced apart or offset from the defined fuselage contour. Display member 20 is disposed on outer surface 40, display member 20 being functionally positioned between inner window member (18) and outer window member (16). By coupling display element 20 to exterior surface 40 of interior window 18 of the passenger compartment, passengers may be prevented from contacting display element 20. In addition, this allows the frame 42 to serve as a support for the display member 20 and electrical connectors (not shown) for transmitting data and power.

Examples of suitable materials for the panels of the exterior and

interior windows

14, 18 may include, but are not limited to, plastic materials (e.g., acrylic polymers). Such as polyacrylates; polyalkylmethacrylates such as polymethyl methacrylate, polyethyl methacrylate, polypropylene methacrylate, stretched acrylic acid, and the like; a polyurethane; a polycarbonate; polyalkylene terephthalates such as polyethylene terephthalate (PET), polypropylene terephthalate, polybutylene terephthalate, and the like; a polysiloxane-containing polymer; or copolymers of any of the monomers used to prepare these, or mixtures thereof); glass, such as conventional soda-lime-silicate glass (the glass may be annealed, heat treated or chemically strengthened); or a combination of any of the above.

The inner window 18 and the outer window 14 are preferably transparent to visible light. By "transparent" is meant having a visible light transmission of greater than 0% up to 100%. Alternatively, one or both of the

panels

12, 18 may be translucent. The display member or inner or outer window member (14, 18) may comprise a film, for example, acting as a polarizer or filter, which filters out certain frequencies of incident light.

Fig. 6-14 illustrate another embodiment for providing a display for the aircraft 10. Referring to fig. 1, 6-9 and 14, as described above, the aircraft 10 includes a fuselage 100 that encloses an aircraft interior 102. The sidewall assembly 104 is incorporated into the fuselage 100. The sidewall assembly 104 includes a sidewall portion 106 of the fuselage 100, the sidewall portion 106 including an inboard face 108 disposed adjacent the aircraft interior 102 and an outboard face 110 disposed adjacent the exterior of the aircraft 10 opposite the inboard face 108.

Referring to fig. 6-9 and 14, in the exemplary embodiment, sidewall assembly 104 includes a plurality of

windows

112 and 114, where the plurality of

windows

112 and 114 are spaced apart and partially or completely surrounded by sidewall portion 106. As shown, the transparent display panel 116 is coupled to the sidewall portion 106, covering the inward facing side 108 of the sidewall portion 106 including

windows

112 and 114. In the exemplary embodiment, transparent display panel 116 includes one or more display screens 118a-b that independently display information (e.g., different information) to passengers 120 within aircraft interior 102. In an exemplary embodiment, transparent display panel 116 is a transparent OLED panel and display screens 118a-b are OLED display screens. In an exemplary embodiment, the transparent display panel 116 has a relatively large screen size of about 55 inches to about 90 inches to facilitate viewing.

Referring also to FIG. 14, in the exemplary embodiment, a display controller 122 communicates with transparent display panel 116 to transmit video/

audio signals

124 and 126 that provide corresponding information to display

screens

118a and 118 b. As shown, the display controller 122 may be controlled by the passenger 120 or other occupant of the aircraft 10 via a user input device 121 (e.g., a handheld controller, a personal computing device, etc.) to instruct the display controller 122 to transmit video/

audio signals

124 and 126 to the

respective display screens

118a and 118 b.

In the exemplary embodiment, display controller 122 is in communication with a Cabin Management System (CMS) 128. Among other functions, the CMS128 is configured to control various cabin environmental functions such as temperature, lighting, kitchen services, and in-flight entertainment, including audio, video, interfaces to personal electronic devices, access to media content storage (audio and video files), satellite television and mobile map devices, and access to remote satellite communications and internet connections. As shown, the CMS128 is in communication with an avionics system 130, an internet gateway 132, and an audio-video database 134, the audio-video database 134 containing a plurality of audio-video information and/or a plurality of movies and providing information to the display controller 122 corresponding to temperature information, security information, audio/video information, movies, financial market information, internet access information, flight information, and/or visual objects external to the aircraft. Independently, the display controller 122 may communicate directly with the audio-video database 134 to access audio-video information and/or movies for communication with one or more of the display screens 118a and/or 118 b. In one example, the display controller 122 accesses the audio/video database 134 (e.g., directly or through the CMS128) to transmit the video/audio signals 124 to the transparent display panel 116 for displaying a movie (e.g., audio/video information) on the display screen 118a, and independently accesses the avionics system 130 (e.g., through the CMS128) to transmit the video/audio signals 126 for displaying flight information on the display screen 118 b.

In an exemplary embodiment, the user input device 121 is used to open and/or close the transparent display panel 116. In one example and as shown in fig. 6 and 14, the transparent display panel 116 turns to an "on state" that activates or powers the display screens 118a and/or 118b to display the corresponding information as described above. In another example and as shown in fig. 7-8, the transparent display panel 116 is turned to a "closed state" in which the transparent display panel 116 is transparent to allow the passenger 120 to see through the transparent display panel 116 the inward facing side 108 of the sidewall portion 106 including the

windows

112 and 114. In this way, when the transparent display panel 116 is in the "closed state," the passenger 120 may clearly view the exterior of the aircraft 10 through the transparent display panel 116 and the

windows

112 and 114.

Referring to fig. 7-14, in the exemplary embodiment, sidewall assembly 104 includes a window covering 136 for each of

windows

112 and 114. The window covering 136 is disposed between the

window

112 or 114 and the transparent display panel 116. Each of the window shades 136 is movable between an open position (as shown in fig. 7-9) and a closed position (as shown in fig. 10 and 12), the window shades 136 being in the open position to allow light to pass between the

windows

112 and 114 and the transparent display panel 116 when the transparent display panel 116 is in the "closed state," and the window shades 136 being in the closed position to block light from passing between the

windows

112 and 114 and the transparent display panel 116 when the transparent display panel 116 is in the "open state," for example, to enhance the viewing effect of the display screens 118 a-b.

To further enhance the viewing effect of the display screens 118a-b, in the exemplary embodiment, the sidewall assembly 104 includes a movable shade panel 138 (e.g., a black opaque panel) for each of the

windows

112 and 114. The movable shade panel 138 is disposed between the corresponding window covering 136 and the transparent display panel 116. In an exemplary embodiment, the display controller 122 is in communication with a shade control 140, the shade control 140 being operatively coupled to the movable shade panel 138 to move the panel 138 between a retracted position (as shown in fig. 7-9) and an extended position (as shown in fig. 10 and 12), the panel 138 being in the retracted position to allow light to pass between the

windows

112, 114 and the transparent display panel 116 when the transparent display panel 116 is in the "closed state"; when the transparent display panel 116 is in the "open state," the panel 138 in the extended position may block light from passing between the

windows

112, 114 and the transparent display panel 116. In this way, with the movable shade panel 138 and window covering 136 in the retracted/open position, the passenger 120 may clearly see the exterior of the aircraft 10 through the transparent display panel 116 and

windows

112, 114. Similarly, with the movable shade panel 138 and window covering 136 in the extended/closed position, the viewing of the passenger 120 by the display screens 118a-b is enhanced because the area behind the transparent display panel 116 is shielded from light by blocking outside light from entering the area behind the display screens 118a-b via the

windows

112 and 114.

In an exemplary embodiment, shade control device 140 is further configured to move window covering 136 between an open position and a closed position. In one example, the display controller 122 transmits command signals to the shade control 142 to move the window shade 136 between the open/retracted position and the closed/extended position independently or with the movable shade panel 138.

Referring to fig. 7-8 and 10-13, in an exemplary embodiment, the sidewall assembly 104 includes a transparent cover 142, the transparent cover 142 being disposed adjacent to and covering the transparent display panel 116. For example, the transparent cover 142 is a plastic sheet formed of a transparent material or an amorphous polymer materialFor example, polymethyl methacrylate (PMMA), polycarbonate (for example,

) And the like.

As shown, the ledge 144 is disposed adjacent the inboard face 108 of the sidewall portion 106, extending below the transparent display panel 116 and the transparent cover 142 toward the aircraft interior 102. In an exemplary embodiment, the ledge 144 is both a functional trim (trim piece) and an aesthetic trim that provides a lower structure for supporting the transparent display panel 116. In addition, the transparent display panel 116 is fixed to the sidewall portion 106 by a fastener 146.

The foregoing description of the embodiments has been presented for the purposes of illustration and description. It is not intended to be exhaustive or to limit the disclosure. Individual elements or features of a particular embodiment are generally not limited to that particular embodiment, but are interchangeable where applicable and can be used in a selected embodiment even if not specifically shown or described. These elements and features may also be varied in many ways. Such variations are not to be regarded as a departure from the disclosure, and all such modifications are intended to be included within the scope of the disclosure.

The exemplary embodiments are provided so that this disclosure will be thorough and will fully convey the scope to those skilled in the art. Numerous specific details are set forth such as examples of specific components, devices, and methods to provide a thorough understanding of embodiments of the present disclosure. It will be apparent to those skilled in the art that specific details need not be employed, that example embodiments may be embodied in many different forms and that neither should be construed to limit the scope of the disclosure. In some exemplary embodiments, well-known processes, well-known device structures, and well-known technologies are not described in detail.

The terminology used herein is for the purpose of describing particular example embodiments only and is not intended to be limiting. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. The terms "comprises," "comprising," "including," and "having," are inclusive and therefore specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. The method steps, processes, and operations described herein are not to be construed as necessarily requiring their performance in the particular order discussed or illustrated, unless specifically identified as an order of performance. It should also be understood that additional or alternative steps may be employed.

When an element or layer is referred to as being "on" or "engaged," "connected," or "coupled" to another element or layer, it may be directly on, engaged, connected, or coupled to the other element or layer, or intervening elements or layers may be present. In contrast, when an element is referred to as being "directly on" or "directly engaged", "directly connected", or "directly coupled" to another element or layer, there may be no intervening elements or layers present. Other words used to describe the relationship between elements (e.g., "between" and "directly between," "adjacent" and "directly adjacent," etc.) should be interpreted in a similar manner. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.

Although the terms first, second, third, etc. may be used herein to describe various elements, components, regions, layers and/or sections, these elements, components, regions, layers and/or sections should not be limited by these terms. These terms may be only used to distinguish one element, component, region, layer or section from another region, layer or section. Terms such as "first," "second," and other numerical terms used herein do not imply a sequence or order unless clearly indicated by the context. Thus, a first element, component, region, layer or section discussed below could be termed a second element, component, region, layer or section without departing from the teachings of the example embodiments.

Spatially relative terms, such as "inner," "outer," "below," "lower," "above," "upper," and the like, may be used herein for ease of description to describe one element or feature's relationship to another element or feature or features as illustrated in the figures. Spatially relative terms may also be intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "below" or "beneath" other elements or features would then be oriented "above" the other elements or features. Thus, the exemplary term "below" can encompass both an orientation of above and below. The device may be otherwise oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

Claims

1. A sidewall assembly for an aircraft, the sidewall assembly comprising:

a window;

a sidewall portion having an inwardly facing side and at least partially surrounding the window.

A transparent display panel coupled to the sidewall portion and covering the inward-facing side of the sidewall portion including the window, the transparent display panel including a display screen configured to display information to a passenger; and

a display controller in communication with the transparent display panel to transmit video/audio signals providing the information to the display screen.

2. The sidewall assembly of claim 1, wherein the transparent display panel is configured to be switchable between an on state causing the display screen to display the information and a off state causing the transparent display panel to be transparent to allow the inward facing side of the sidewall portion including the window to be visible to the occupant through the transparent display panel.

3. The sidewall assembly of claim 1, further comprising at least one additional window, wherein the sidewall portion at least partially surrounds the at least one additional window, and wherein the transparent display panel covers the at least one additional window.

4. The sidewall assembly of claim 1, wherein the transparent display panel comprises at least one additional display screen configured to display additional information to the occupant, and wherein the display controller is in communication with the transparent display panel to transmit at least one additional video/audio signal providing the additional information to the at least one additional display screen.

5. The sidewall assembly of claim 1, further comprising a transparent cover disposed adjacent to and covering the transparent display panel.

6. The sidewall assembly of claim 1, further comprising a ledge disposed adjacent the inward facing side of the sidewall portion extending from below the transparent display panel.

7. The sidewall assembly of claim 1, wherein the transparent display panel has a screen size of about 55 to about 90 inches.

8. The sidewall assembly of claim 1, further comprising a window curtain disposed between the window and the transparent display panel and movable between an open position that allows light to pass between the window and the transparent display panel and a closed position that blocks light from passing between the window and the transparent display panel.

9. The sidewall assembly of claim 1, further comprising:

a movable shading panel disposed between the window and the transparent display panel; and

a shading control device configured to move the movable shading panel between a retracted position that allows light to pass between the window and the transparent display panel and an extended position that blocks light from passing between the window and the transparent display panel.

10. The sidewall assembly of claim 9, wherein the display controller is configured to provide a command signal to the shade control device to move the movable shade panel between the retracted position and the extended position.

11. An aircraft, comprising:

a fuselage surrounding an aircraft interior and including a sidewall portion having an inwardly facing side disposed adjacent the aircraft interior;

a window disposed in the fuselage and at least partially surrounded by the sidewall portion;

a transparent display panel coupled to the sidewall portion and covering the inward-facing side of the sidewall portion including the window, the transparent display panel including a display screen configured to display information to passengers of the aircraft interior; and

12. The aircraft of claim 11, further comprising a Cabin Management System (CMS) in communication with the display controller to provide the information to the display controller, wherein the information comprises one of temperature information, security information, audio/video information, movies, financial market information, internet access information, flight information, off-aircraft visuals, and combinations thereof.

13. The aircraft of claim 12, further comprising an audio/video database containing information corresponding to one of the audio/video information, a plurality of movies, and combinations thereof, and wherein one of the display controller and the CMS communicates with the audio/video database to receive the information.

14. The aircraft of claim 11, wherein the transparent display panel is configured to be switchable between an on state causing the display screen to display the information and an off state causing the transparent display panel to be transparent to allow the inward facing side of the sidewall portion including the window to be visible to the occupant through the transparent display panel.

15. The aircraft of claim 14, further comprising a curtain disposed between the window and the transparent display panel and movable between an open position in which light may be allowed to pass between the window and the transparent display panel when the transparent display panel is in a closed state and a closed position in which light may be blocked from passing between the window and the transparent display panel when the transparent display panel is in an open state.

16. The aircraft of claim 15, further comprising:

a movable shade panel disposed between the window covering and the transparent display panel; and

a shade control device configured to move the movable shade panel between a retracted position and an extended position, the movable shade panel in the retracted position allowing light to pass between the window and the transparent display panel when the transparent display panel is in the closed state, the movable shade panel in the extended position blocking light from passing between the window and the transparent display panel when the transparent display panel is in the open state.

17. The aircraft of claim 16, wherein the shade control device is further configured to move the window covering between the open position and the closed position.

18. The aircraft of claim 17, wherein the display controller is configured to provide command signals to the shade control device to move at least one of the movable shade panel and the window covering.

19. The aircraft of claim 11, wherein the sidewall portion at least partially surrounds at least one additional window, and wherein the transparent display panel covers the at least one additional window.

20. The aircraft of claim 11, further comprising:

a transparent cover disposed adjacent to and covering the transparent display panel; and

a ledge disposed adjacent to the inward facing side of the sidewall portion extending below the transparent display panel and the transparent cover.